CN205176666U - Solar energy multiaxis aircraft - Google Patents
Solar energy multiaxis aircraft Download PDFInfo
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- CN205176666U CN205176666U CN201520863995.4U CN201520863995U CN205176666U CN 205176666 U CN205176666 U CN 205176666U CN 201520863995 U CN201520863995 U CN 201520863995U CN 205176666 U CN205176666 U CN 205176666U
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- axis aircraft
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- steering
- steering mechanism
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Abstract
The utility model provides a solar energy multiaxis aircraft, including multiaxis aircraft main part and solar cell panel a steering system, solar cell panel a steering system includes solar panel, a plurality of branch and a plurality of steering mechanism, and a plurality of branches are passed through steering mechanism and are connected and constitute folding bracket, and folding bracket's one end is passed through steering mechanism and is connected in multiaxis aircraft main part, and the other end passes through steering mechanism and is connected with solar panel. Still including taking down the exhibits control system for control solar cell panel packing up or expanding. The utility model discloses increased solar cell panel's the function that turns to, made day function that chases after that solar cell panel has, guaranteed solar cell panel's face and the Sun's rays's verticality, improved the use of solar energy and rateed, and then can prolong the flight time of multiaxis aircraft. And solar cell panel can pack up to the main support lower part of multiaxis aircraft, can reduce the flight resistance of strong wind weather, improves the flight stability of aircraft.
Description
Technical field
The utility model relates to Multi-axis aircraft technical field, especially sun power Multi-axis aircraft.
Background technology
Because Multi-axis aircraft structure is simple, and the control of Multi-axis aircraft is also comparatively simple, and its flying quality is all more stable, makes Multi-axis aircraft be easy to miniaturization, and application popularization speed in recent years improves greatly.Now common Multi-axis aircraft is two axles, three axles, four axles, five axles, six axles and eight axle aircraft, also has the Multi-axis aircraft of more multiaxis, but the most commonly four-axle aircraft.
The energy of Multi-axis aircraft is the factor affecting its flight time always, also governs its application in some field.Therefore, occurred having set up the Multi-axis aircraft of solar energy photovoltaic system, in flight course, electric energy that sun power transforms can have been utilized as the energy, extend the flight time of aircraft.But the setting of the solar panel in current sun power Multi-axis aircraft is fixing, and angle can not adjust, and can not make full use of sun power.And when running into strong wind sky, solar panel adding lifting surface area, causing the flight resistance of aircraft to become large, increasing energy consumption of electrical machinery, even affect the flight stability of aircraft.
Utility model content
The purpose of this utility model is to provide sun power Multi-axis aircraft, and the solar panel solving existing sun power Multi-axis aircraft, for being fixedly installed, causes solar energy utilization ratio low, and the technical matters causing flight resistance to increase when strong wind sky.
In order to achieve the above object, the utility model provides following technical scheme:
Sun power Multi-axis aircraft, comprise Multi-axis aircraft main body and solar panel steering, described solar panel steering comprises solar panels, multiple pole and multiple steering mechanism, described multiple pole connects and composes Collapsible rack by steering mechanism, one end of described Collapsible rack is connected in described Multi-axis aircraft main body by steering mechanism, and the other end is connected with described solar panels by steering mechanism.
Further, described solar panel steering also comprises turning control cell and turn signal generating unit, the output terminal of described turning control cell be connected with the control end of multiple described steering mechanism respectively, input end is connected with described turn signal generating unit.Turning control cell receives the turn signal that turn signal generating unit exports, then steering order is sent according to this turn signal respectively to the control end of multiple described steering mechanism, control steering mechanism to rotate, conversion solar panel towards all the time towards the sun, increase and shine upon area, improve the utilization factor of sun power.
Particularly, described turn signal generating unit can be the steering controller with turning control cell wireless connections.Course changing control is carried out by the personnel in terrestrial operation.
Particularly, described turn signal generating unit can be optical sensor, and the induction end of described optical sensor is arranged on solar panel, and output terminal is connected with the input end of described turning control cell.In the flight course of Multi-axis aircraft, utilize optical sensor to monitor the change of solar light on solar panel in real time, thus control turning to of solar panel.What adopt which can improve solar panel turns to degree of accuracy, improves solar energy utilization ratio further.
Particularly, described steering mechanism adopts existing single shaft tracking apparatus or double-axis tracking device.
Further, described sun power Multi-axis aircraft also comprises solar panel and to take down the exhibits control system, and solar panel control system of taking down the exhibits comprises take down the exhibits control module and signal generating unit of taking down the exhibits; The output terminal of described control module of taking down the exhibits is connected with the control end of multiple described steering mechanism respectively, and input end is connected with described signal generating unit of taking down the exhibits.Signal generating unit of taking down the exhibits sends to control module of taking down the exhibits to be packed up or deployment signal, and after control module of taking down the exhibits receives this signal, send instruction to multiple described steering mechanism, steering mechanism carries out corresponding action, is packed up by solar panel or launches.
Particularly, signal generating unit of taking down the exhibits described in can be the controller of taking down the exhibits with control module wireless connections of taking down the exhibits.Course changing control is carried out by the personnel in terrestrial operation.
Particularly, described in signal generating unit of taking down the exhibits can be wind sensor, the induction end of described wind sensor is arranged on solar panel, and output terminal is connected with the input end of described control module of taking down the exhibits.Wind sensor induction wind-force size, when wind-force exceedes preset value, sends to control module of taking down the exhibits and packs up signal, and control module of taking down the exhibits receives after this packs up signal, sends instruction, packed up by solar panel to each steering mechanism.Real-time according to wind-force size, solar panel is packed up or launches.
Further, described solar panel steering adopts the many cover solar panel steering the same with the quantity of the fulcrum of Multi-axis aircraft main body, often overlaps described solar panel steering and is arranged between adjacent two axles of described Multi-axis aircraft main body.
Further, described pole is at least two, and two poles connect and compose Collapsible rack by steering mechanism.
Sun power Multi-axis aircraft of the present utility model adds the turning function of solar panel, the solar tracking function that solar panel is had, ensure that the plate face of solar panel and the perpendicularity of sunray, improve the utilization factor of sun power, and then the flight time of Multi-axis aircraft can be extended.And solar panel can pack up the main support bottom to Multi-axis aircraft, can reduce flight resistance during strong wind sky, improve the flight stability of aircraft.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of the utility model sun power Multi-axis aircraft;
Fig. 2 be in Fig. 1 A-A to cross-sectional view;
Fig. 3 is cross-sectional view when solar panel is packed up in the utility model sun power Multi-axis aircraft.
Embodiment
Below in conjunction with accompanying drawing of the present utility model, be clearly and completely described the technical solution of the utility model, obviously, described embodiment is only the utility model part embodiment, instead of whole embodiments.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
According to Fig. 1, Fig. 2 and Fig. 3, sun power Multi-axis aircraft of the present utility model is described, comprise Multi-axis aircraft main body 1 and solar panel steering 2, described solar panel steering 2 comprises solar panels 21, multiple pole 22 and multiple steering mechanism 23, described multiple pole 22 connects and composes Collapsible rack by steering mechanism 23, one end of described Collapsible rack is connected in described Multi-axis aircraft main body 1 by steering mechanism 23, and the other end is connected with described solar panels 21 by steering mechanism 23.
Described Collapsible rack is connected and composed by steering mechanism 23 by least two poles 22.The quantity of pole is more, and course changing control is more accurate, but controls more complicated, therefore, is preferably the Collapsible rack that employing two poles 22 are formed.
Particularly, described steering mechanism 23 adopts existing single shaft tracking apparatus or double-axis tracking device.
In order to can to solar panel in the flight course of Multi-axis aircraft towards adjusting, described solar panel steering 2 also comprises turning control cell 24 and turn signal generating unit 25, and described turning control cell 24 is fixed on the main support 11 of Multi-axis aircraft main body 1.The output terminal of described turning control cell 24 be connected with the control end of multiple described steering mechanism 23 respectively; Input end is connected with described turn signal generating unit 25.
Described turn signal generating unit 25 can be the steering controller (not shown) with turning control cell 24 wireless connections.Course changing control is carried out by the personnel in terrestrial operation.Also can be shown in optical sensor 25, Fig. 2, its induction end be fixedly installed on solar panel 21, and output terminal is connected with the input end of described turning control cell 24.In the flight course of Multi-axis aircraft, utilize optical sensor to monitor the change of solar light on solar panel in real time, thus control turning to of solar panel.What adopt which can improve solar panel turns to degree of accuracy, improves solar energy utilization ratio further.
In order to keep the in-flight balance of Multi-axis aircraft, the steering 2 of solar panel described in the utility model adopts the many cover solar panel steering 2 the same with the quantity of the fulcrum 12 of Multi-axis aircraft main body 1, often overlaps described solar panel steering 2 and is arranged between adjacent two fulcrums 12 of described Multi-axis aircraft main body 1.
Multi-axis aircraft is in flight course, and the impact of by wind is larger.Especially, after having set up solar panel, because the area of Multi-axis aircraft increases, in flight course, the impact of wind-force on it is more obvious.Therefore, Multi-axis aircraft of the present utility model also comprises solar panel and to take down the exhibits control system, and solar panel control system of taking down the exhibits comprises take down the exhibits control module 31 and signal generating unit 32 of taking down the exhibits; The output terminal of described control module 31 of taking down the exhibits is connected with the control end of multiple described steering mechanism 23 respectively, and input end is connected with described signal generating unit 32 of taking down the exhibits.Signal generating unit 32 of taking down the exhibits sends to control module 31 of taking down the exhibits to be packed up or deployment signal, after control module 31 of taking down the exhibits receives this signal, send instruction to multiple described steering mechanism 23, steering mechanism 23 carries out corresponding action, and solar panel 21 is packed up or launched.State after being packed up by solar panel as shown in Figure 3.
Particularly, signal generating unit of taking down the exhibits described in can be the controller (not shown) of taking down the exhibits with control module wireless connections of taking down the exhibits.Course changing control is carried out by the personnel in terrestrial operation.Also can be wind sensor 32, the induction end of described wind sensor 32 be arranged on solar panel 21, and output terminal is connected with described input end of taking down the exhibits control module 31.Wind sensor 32 responds to wind-force size, when wind-force exceedes preset value, sends pack up signal to control module 31 of taking down the exhibits, and control module 31 of taking down the exhibits receives after this packs up signal, sends instruction, packed up by solar panel 21 to each steering mechanism 23.Real-time according to wind-force size, solar panel 21 is packed up or launched.
The above; be only embodiment of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; change can be expected easily or replace, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should described be as the criterion with the protection domain of claim.
Claims (10)
1. sun power Multi-axis aircraft, it is characterized in that, comprise Multi-axis aircraft main body and solar panel steering, described solar panel steering comprises solar panels, multiple pole and multiple steering mechanism, described multiple pole connects and composes Collapsible rack by steering mechanism, one end of described Collapsible rack is connected in described Multi-axis aircraft main body by steering mechanism, and the other end is connected with described solar panels by steering mechanism.
2. sun power Multi-axis aircraft according to claim 1, it is characterized in that, described solar panel steering also comprises turning control cell and turn signal generating unit, the output terminal of described turning control cell is connected with the control end of multiple described steering mechanism respectively, and input end is connected with described turn signal generating unit.
3. sun power Multi-axis aircraft according to claim 2, is characterized in that, described turn signal generating unit is the steering controller with turning control cell wireless connections.
4. sun power Multi-axis aircraft according to claim 2, is characterized in that, described turn signal generating unit is optical sensor, and the induction end of described optical sensor is arranged on solar panel, and output terminal is connected with the input end of described turning control cell.
5. sun power Multi-axis aircraft according to claim 1, it is characterized in that, described sun power Multi-axis aircraft also comprises solar panel and to take down the exhibits control system, and solar panel control system of taking down the exhibits comprises take down the exhibits control module and signal generating unit of taking down the exhibits; The output terminal of described control module of taking down the exhibits is connected with the control end of multiple described steering mechanism respectively, and input end is connected with described signal generating unit of taking down the exhibits.
6. sun power Multi-axis aircraft according to claim 5, is characterized in that, described in signal generating unit of taking down the exhibits be the controller of taking down the exhibits with control module wireless connections of taking down the exhibits.
7. sun power Multi-axis aircraft according to claim 5, it is characterized in that, described signal generating unit of taking down the exhibits is wind sensor, and the induction end of described wind sensor is arranged on solar panel, and output terminal is connected with the input end of described control module of taking down the exhibits.
8. sun power Multi-axis aircraft according to any one of claim 1 to 7, is characterized in that, described steering mechanism adopts single shaft tracking apparatus or double-axis tracking device.
9. sun power Multi-axis aircraft according to any one of claim 1 to 7, it is characterized in that, described solar panel steering adopts the many cover solar panel steering the same with the quantity of the fulcrum of Multi-axis aircraft main body, often overlaps described solar panel steering and is arranged between adjacent two fulcrums of described Multi-axis aircraft main body.
10. sun power Multi-axis aircraft according to any one of claim 1 to 7, is characterized in that, described pole is at least two, and two poles connect and compose Collapsible rack by steering mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520863995.4U CN205176666U (en) | 2015-10-30 | 2015-10-30 | Solar energy multiaxis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520863995.4U CN205176666U (en) | 2015-10-30 | 2015-10-30 | Solar energy multiaxis aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205176666U true CN205176666U (en) | 2016-04-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520863995.4U Expired - Fee Related CN205176666U (en) | 2015-10-30 | 2015-10-30 | Solar energy multiaxis aircraft |
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| CN (1) | CN205176666U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114884A (en) * | 2016-06-28 | 2016-11-16 | 安庆市佰斯特电子科技有限公司 | A kind of unmanned plane based on Stewart parallel institution stops charging station |
| CN106184728A (en) * | 2016-07-08 | 2016-12-07 | 武汉科技大学 | A kind of rotary telescopic variable-torque quadrotor |
| CN108820229A (en) * | 2018-06-22 | 2018-11-16 | 李帷笳 | Hybrid power unmanned plane based on computer mode control |
| CN109515676A (en) * | 2019-01-09 | 2019-03-26 | 中国人民解放军国防科技大学 | Retractable solar cell system suitable for stratospheric airship |
| CN111555696A (en) * | 2020-05-16 | 2020-08-18 | 金栋 | Supporting mechanism of solar panel |
| US20210229805A1 (en) * | 2019-04-01 | 2021-07-29 | Getman Anya L | Drone including a piezoelectric structure and/or a self-energizing capability |
| CN113830313A (en) * | 2021-09-26 | 2021-12-24 | 沈阳航空航天大学 | Folding solar aircraft and control method thereof |
| US11948703B2 (en) | 2019-04-01 | 2024-04-02 | Anya L. Getman | Methods and devices for electrically insulating a power line |
-
2015
- 2015-10-30 CN CN201520863995.4U patent/CN205176666U/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106114884A (en) * | 2016-06-28 | 2016-11-16 | 安庆市佰斯特电子科技有限公司 | A kind of unmanned plane based on Stewart parallel institution stops charging station |
| CN106114884B (en) * | 2016-06-28 | 2018-07-10 | 谢爱珠 | A kind of unmanned plane based on Stewart parallel institutions stops charging station |
| CN106184728A (en) * | 2016-07-08 | 2016-12-07 | 武汉科技大学 | A kind of rotary telescopic variable-torque quadrotor |
| CN108820229A (en) * | 2018-06-22 | 2018-11-16 | 李帷笳 | Hybrid power unmanned plane based on computer mode control |
| CN108820229B (en) * | 2018-06-22 | 2021-10-08 | 河南医学高等专科学校 | Hybrid unmanned aerial vehicle based on computer state control |
| CN109515676A (en) * | 2019-01-09 | 2019-03-26 | 中国人民解放军国防科技大学 | Retractable solar cell system suitable for stratospheric airship |
| US20210229805A1 (en) * | 2019-04-01 | 2021-07-29 | Getman Anya L | Drone including a piezoelectric structure and/or a self-energizing capability |
| US11948703B2 (en) | 2019-04-01 | 2024-04-02 | Anya L. Getman | Methods and devices for electrically insulating a power line |
| CN111555696A (en) * | 2020-05-16 | 2020-08-18 | 金栋 | Supporting mechanism of solar panel |
| CN111555696B (en) * | 2020-05-16 | 2021-03-19 | 威海汇晟智能装备有限公司 | Supporting mechanism of solar panel |
| CN113830313A (en) * | 2021-09-26 | 2021-12-24 | 沈阳航空航天大学 | Folding solar aircraft and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160420 Termination date: 20161030 |
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| CF01 | Termination of patent right due to non-payment of annual fee |